J40-001 Issue 05 - Cabri G2 Flight Manual

FLIGHT TIME MANAGEMENT................................................................................4-14 APPROACH AND LANDING ..................................................................................4-15 ENGINE / ROTOR SHUTDOWN ............................................................................4-16 DISENGAGEMENT WITH ENGINE OFF..................................................................4-16 TRAINING .........................................................................................................4-17 SECTION 5 PERFORMANCE...........................................................................5-I AIRSPEED CALIBRATION ......................................................................................5-1 ROTOR STARTING AND STOPPING LIMIT ................................................................5-2 HEIGHT-VELOCITY DIAGRAM ................................................................................5-3 HOVER OUT OF GROUND EFFECT ........................................................................5-4 HOVER IN GROUND EFFECT ................................................................................5-5 RATE OF CLIMB AT VY = 50 KT IAS ......................................................................5-6 TAKE OFF DISTANCE..........................................................................................5-10 GLIDE DISTANCE IN AUTOROTATION ...................................................................5-10 SOUND EXPOSURE LEVEL ..................................................................................5-10 SECTION 6 WEIGHT AND BALANCE ..............................................................6-I GENERAL ...........................................................................................................6-1 CENTER OF GRAVITY, STANDARD DEFINITIONS .....................................................6-3 HELICOPTER WEIGHING PROCEDURE ...................................................................6-4 WEIGHT AND CG POSITION DETERMINATION.........................................................6-7 SECTION 7 SYSTEMS DESCRIPTION ............................................................7-I AIRFRAME ..........................................................................................................7-1 DYNAMIC SYSTEMS .............................................................................................7-2 ENGINE INSTALLATION.........................................................................................7-5 ELECTRICAL CIRCUIT...........................................................................................7-7 ELECTRONIC PILOT MONITOR - EPM .................................................................7-11 BARC ..............................................................................................................7-17 OTHER EQUIPMENTS .........................................................................................7-18 CABIN AND AMENITIES .......................................................................................7-20 SECTION 8 HANDLING AND SERVICING .......................................................8-I GENERAL ...........................................................................................................8-1 FUEL ..................................................................................................................8-1 ENGINE OIL.........................................................................................................8-1 GEARBOXES OIL .................................................................................................8-1 GROUND HANDLING ............................................................................................8-1 PARKING AND TIE-DOWN .....................................................................................8-2 JUMP-STARTING THE ENGINE ...............................................................................8-2 DOORS REMOVAL AND INSTALLATION ...................................................................8-2 SECTION 9 SUPPLEMENTS Issue 05 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-1 Section 0 Introduction This document is the Pilot Operating Handbook and EASA approved rotorcraft Flight Manual of the CABRI G2 Rotorcraft. The following tables give the list of approved pages and the list of changes. For flight manual supplements tables (approved pages and revisions log), refer to Section 9. The following table gives EASA approved pages. Page number Revision number Page number Revision number 2-1 05 2-i 03 2-2 05 2-ii 2-3 2-4 05 2-5 01 2-6 2-7 03 2-8 05 2-9 05 2-10 03 2-11 2-12 02 2-13 05 Section 2 Limitations 2-14 3-1 3-i 3-2 3-ii 3-3 3-4 05 3-5 01 3-6 3-7 03 3-8 05 3-9 05 3-10 01 3-11 03 3-12 03 3-13 03 3-14 05 3-15 05 Section 3 Emergency procedures 3-16 05 Issue 05 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-2 Approved under DOA EASA.21J.211 Original issue Page number Revision number Page number Revision number 4-1 4-i 03 4-2 02 4-ii 4-3 02 4-4 4-5 05 4-6 4-7 02 4-8 05 4-9 05 4-10 4-11 05 4-12 05 4-13 4-14 4-15 03 4-16 05 4-17 4-18 4-19 03 Section 4 Normal procedures 4-20 05 5-1 5-i 5-2 5-ii 5-3 5-4 05 5-5 05 5-6 05 5-7 5-8 05 5-9 Section 5 Performance 5-10 Issue 05 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-3 The following table gives the pages approved under DOA EASA.21J.211 : Page number Revision number Page number Revision number Cover A B C 03 Table of content D 05 0-1 05 0-7 05 0-2 05 0-8 05 0-3 05 0-4 05 0-5 02 Section 0 Introduction 0-6 02 1-1 1-i 03 1-2 1-ii 1-3 03 1-4 1-5 Section 1 General 1-6 6-1 03 6-i 6-2 6-ii 6-3 6-4 05 6-5 05 6-6 6-7 05 Section 6 Weight and balance 6-8 05 7-1 7-i 03 7-2 7-ii 7-3 03 7-4 7-5 02 7-6 7-7 02 7-8 05 7-9 05 7-10 02 7-11 03 7-12 02 7-13 03 Section 7 Systems description 7-14 Issue 05 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-4 Approved under DOA EASA.21J.211 Original issue Page number Revision number Page number Revision number 7-15 01 7-16 03 7-17 03 7-18 03 7-19 03 7-20 03 8-1 05 8-i 05 8-2 05 8-ii 8-3 05 Section 8 Handling and servicing 8-4 05 Issue 05 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-5 The reference of this flight manual is J40-001. The revisions are given in the following table : Revision number Page Revision object Approval date Approval reference (*) - - Original issue 14/12/2007 TC EASA.R.145 approved by EASA letter D(2007) CPRO/ALE/55199 3-10 4-12 Carb heat manual test transferred to section 4 4-9 4-11 Normal procedure correction 4-15 Steep descent procedure suppressed 3-5 3-15 4-9 4-11 17/09/2008 EASA.R.A.01530 7-8 Addition of a STARTER caution light 7-9 Breaker panel update 7-15 16/09/2008 Approved under the authority of DOA EASA.21J.211 01 2-5 Low fuel indication warning 17/09/2008 EASA.R.A.01530 9-1 GPS 19/05/2009 Approved under DOA EASA.21J.211 according to FSA-09-003 9-2 to 9-4 Night VFR 19/05/2009 EASA.R.C.03230 9-5 to 9-10 Night VFR 19/05/2009 Approved under DOA EASA.21J.211 according to FSA-09-003 2-10 Gage → charge 3-15 Clutch light 4-2 4-9 4-11 4-12 4-16 Procedure update 19/05/2009 EASA.R.C.03230 02 1-3 Drive line → gearbox 19/05/2009 DOA EASA.21J.211 (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Issue 02 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-6 Approved under DOA EASA.21J.211 Original issue (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Revision number Page Revision object Approval date Approval reference (*) 4-3 4-7 Tight → Lockwiring 4-5 Manifold → distributor 4-9 Note suppression 19/05/2009 EASA.R.C.03230 7-5 Modified clutching system description 7-8 7-10 Typos : - battery breaker order - Auxiliaries is push-pull 7-7 to 7-9 & 2-12 Note for optionals 7-10 Battery breaker drawing correction. Add on ELT use. 7-12 Explanation of EPM restart in welcome page 7-13 Note for brightness equalization 7-16 Explanation of re- initiation of testing sequence 02 7-18 Code procedure update Note update 19/05/2009 Approved under the authority of DOA EASA.21J.211 according to FSA-09-003 Issue 02 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-7 Revision number Page Revision object Approval date Approval reference (*) This issue is associated with MOD EPM 10-009. 2.4 Oil P. indicator 2-7 MLI supplements 2-10 Carb. Heat proc 2-13 Addition of socket 3-7 Note update 3-11 3-12 Carb heat 3-13 3-14 Oil P yellow zone Carb heat suppr. 4-12 4-15 Carb. Heat proc. 4-19 Proc. correction. 9-1 Limitation update. 21/07/2010 EASA.R.C.03496 Major modification approval 10031011 6-1, 1-3, 1-i, 7-i, 7-3, C, D Wording 7-11 7- 13 Screenshot update 7-16 >7- 20 Carb heat, pages shift 03 7-18 Ref to night lights 07/06/2010 Approved under DOA EASA.21J.211 according to FSA 10-003. 04 D, 0-1 to 0-4, Section 9 Supplements are managed independently 05/11/2010 Approved under DOA EASA.21J.211 according to FSA 10-011. 2-2, 4- 9/11, 5-4 to -6, 5-8 -20°C extension 05 3-4/5/8/9 3-14 - 16 4-5/8/16 4-20, 2-4 Procedure update 13/12/2010 Major modification approval 10032992 Issue 05 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-8 Approved under DOA EASA.21J.211 Original issue (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Revision number Page Revision object Approval date Approval reference (*) 2-8/9 CG Update 2-13 Correction 13/12/2010 Major modification approval 10032992 D, 2-1, 0-1/2/3/5 0-7, 7-8, 7-9, 8-1 Update 6-4/5 Level measurement 6-7/8 Fuel CG Correction 7-10 Direct battery breaker correction 05 8-i, 8-1 à 4 Doors removal 13/12/2010 Approved under DOA EASA.21J.211 according to FSA 10-018 Issue 05 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-i Section 1 General INTRODUCTION.............................................................................................. 1-1 THREE-VIEW OF THE CABRI G2..................................................................... 1-2 DESCRIPTIVE DATA ........................................................................................ 1-3 Main rotor............................................................................................... 1-3 Tail rotor................................................................................................. 1-3 Transmission.......................................................................................... 1-3 Powerplant ............................................................................................. 1-4 Fuel........................................................................................................ 1-4 SYMBOLS AND ABBREVIATIONS ....................................................................... 1-5 CONVERSION FACTORS .................................................................................. 1-6 Metric to Imperial units........................................................................... 1-6 Imperial to metric units........................................................................... 1-6 Issue 03 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-ii Approved under DOA EASA.21J.211 Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-1 Introduction This Flight Manual is designed as an operating guide for the pilot. It includes material required to be furnished to the pilot by EASA CS 27 and Part 21. It also contains supplementary data supplied by the helicopter manufacturer. This manual is intended to give the pilot the best possible information and to help him find the best answer to most operational situation. However, it cannot replace pilot’s appreciation of each particular situation. Pilot must maintain adequate ground and flight instruction, and good proficiency in the type of helicopter. To achieve the required level of safety, the helicopter pilot-in-command must be familiar with this manual’s content, with other safety-related available information, and with all the regulation covering aircraft operation that are relevant in the country of operation. He is responsible for determining that the helicopter is safe for flight, and for operating it in respect to this manual and above information. The helicopter’s owner is responsible for maintaining the aircraft in approved airworthy condition and for maintaining this manual in a current status in accordance with the list of current pages. Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-2 Approved under DOA EASA.21J.211 Original issue Three-view of the CABRI G2 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-3 Descriptive data Main rotor Type ............................................................. Articulated, soft-in-plane Number of blades ................................................................................. 3 Diameter...................................................................................... 7,20 m (23.6 feet) Nominal rotor speed ................................................................ 530 RPM Blade chord ............................................................................... 180 mm (7.1 in) Tail rotor Type .......................................................................................Shrouded Number of blades ................................................................................. 7 Diameter.................................................................................... 600 mm (23.6 in) Nominal rotor speed .............................................................. 5148 RPM Blade chord ................................................................................. 42 mm (1.6 in) Transmission Primary transmission ........................................................................Belt 0.855/1 reducing ratio Main rotor gearbox .....................................................Spiral bevel gear 11/47 reducing ratio Tail rotor gearbox .......................................................Spiral bevel gear 25/11 increasing ratio Issue 03 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-4 Approved under DOA EASA.21J.211 Original issue Powerplant Model ..................................................... Textron Lycoming O360-J2A with STC EASA.E.S.01001 Type .......................... Four cylinders, horizontally opposed, direct drive, air cooled, normally-aspirated, carburetor-equipped, one magneto and one electronic ignition system Displacement ..................................................................................5,9 L (361 cu.in) Power rating (continuous) .............108 kW @ 2585 through 2700 RPM (145 shp) Nominal speed .......................................................................2650 RPM Cooling system ............................... Direct drive squirrel-cage blower Ignition systems Magneto ......................................................................................Bendix Electronic ignition system.......................................... LSE Plasma II HG Solid-state capacitor discharge ignition system Variable timing advance Fuel Maximum fuel capacity ..................................................................170 L (45 U.S. gal) Unusable fuel ..................................................................................1.5 L (0.4 U.S. gal) Approved fuel grade.................................................................... 100 LL Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-5 Symbols and abbreviations Symbol or abbreviation Designation Speeds CAS ......................................................................... Calibrated airspeed IAS............................................................................. Indicated airspeed TAS .................................................................................. True airspeed VNE......................................................................... Never-exceed speed Vy .....................................................................Best rate-of-climb speed Meteorology ISA....................................................International standard atmosphere OAT ...................................................................Outside air temperature P ............................................................................. Outside air pressure σ ............................................................................... Relative air density Altitude / Height AGL ..........................................................................Above ground level Z ................................................................................ Geometric altitude Zp ................................................................................ Pressure altitude Zσ ......................................................................Relative density altitude h .................................................................................. Geometric height Power / Engine parameters FLO ..................................................... First MLI limit is Full throttle limit MCP ...........................................................Maximum continuous power MLI ....................................................................... Multiple limit indicator NR .......................................................................................Rotor speed NM.................................................................................... Engine speed PWR ............................................................ First MLI limit is Power limit Hover / Take-off / Landing IGE ................................................................................ In ground effect OGE ........................................................................Out of ground effect HIGE.................................................................... Hover in ground effect HOGE............................................................ Hover out of ground effect Weight and balance CG ................................................................................ Centre of gravity MTOW .............................................................Maximum take-off weight Equipment EPM....................................................................Electronic Pilot Monitor BARC ................................................ Boîtier Alarme Rotor et Carburant (Fuel and rotor alarm device) RRM / GOV ................................................................. Engine governor Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-6 Approved under DOA EASA.21J.211 Original issue Miscellaneous BB .................................................................................. Battery breaker H/V..................................................................................Height-Velocity MGB.................................................................................. Main gearbox RPM................................................................... Revolutions per minute TGB .................................................................................... Tail gearbox VFR..............................................................................Visual flight rules Conversion factors Note : The Cabri G2 EPM display can be set to either Metric or Imperial units. Refer to page 7-13. Metric to Imperial units Multiply .......................................By......................................To obtain millimeters (mm) .......................... 0,0394 .............................. inches (in) meters (m).................................... 3,2808 ................................... feet (ft) kilometers (km) ............................ 0,5400 .................nautical miles (nm) kilograms (kg) .............................. 2,2046 .............................pounds (lb) liters (L)........................................ 0,2642 .......... gallons, U.S. (U.S. gal) liters (L)........................................ 1,0567 .............................. quarts (qt) millibar (mbar) .............................. 0,0295 ....... inches of mercury (in.hg) bars (bar) ................................... 14,5038 . pounds per square inch (psi) Imperial to metric units Multiply .......................................By......................................To obtain inches (in) ...................................... 25,40 .................... millimeters (mm) feet (ft) ......................................... 0,3048 ............................. meters (m) nautical miles (nm)....................... 1,8520 ...................... kilometers (km) pounds (lb) ................................... 0,4536 ........................ kilograms (kg) gallons, U.S. (U.S. gal) ................ 3,7854 ..................................liters (L) quarts (qt)..................................... 0,9464 ..................................liters (L) inches of mercury (in.hg)................ 33,86 ........................ millibar (mbar) pounds per square inch (psi)........ 0,0689 ................................. bar (bar) 1013,25 mbar = 29.92 in.hg Temperature Fahrenheit degrees / Celsius degrees F = 32 .C 5 9 + C = 32) .(F 9 5 − Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-i Section 2 Limitations GENERAL LIMITATIONS ................................................................................... 2-1 COLOR CODE FOR INSTRUMENT MARKINGS....................................................... 2-1 FLIGHT ENVELOPE LIMITATIONS ....................................................................... 2-2 Altitude limitation.................................................................................... 2-2 Outside air temperature limitation .......................................................... 2-2 Airspeed limits........................................................................................ 2-2 Rotor speed limits .................................................................................. 2-3 POWERPLANT LIMITATIONS ............................................................................. 2-4 TRANSMISSION LIMITATIONS ........................................................................... 2-7 WEIGHT AND BALANCE LIMITATIONS (METRIC UNITS).......................................... 2-9 SENSORS FAILURES..................................................................................... 2-10 PLACARDS.................................................................................................. 2-11 Issue 03 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-ii EASA Approved Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-1 The information in section 2, Limitations, is approved by EASA. General limitations Only day VFR is approved. Aerobatic flight is prohibited. Voluntary in-flight engine shut down is prohibited. Flight in known icing conditions is prohibited. Flight under snow is prohibited. Minimum crew is one pilot on the right seat. Left seat harness must be buckled when seat is empty. In this case, left controls removal is recommended. Operation is approved with the left seat removed, only if the left controls are removed. Operation is approved with either or both doors removed, or unlocked and partially open for ventilation. In these cases, no loose object is allowed in the cabin. Speed limitations are the same than ones with doors installed and closed. Color code for instrument markings Red Indicates operating limits. The pointer should not enter red zones or exceed red limits during normal operation. Red cross -hatch Indicates power-off VNE Yellow or amber Precautionary or special operating procedure range Green Normal operating range White or Blue Other indications On the EPM, related numerical values are marked with the same color code. Issue 05 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-2 EASA Approved Original issue Flight envelope limitations Altitude limitation Maximum operating altitude (Zp) ............................................. 13 000 ft Outside air temperature limitation Maximum temperature ..........................................................ISA + 30°C limited to + 45°C Minimum operating temperature ................................................. - 20°C Minimum storage temperature .................................................... - 30°C Airspeed limits VNE power-on .........................................................................130 kt IAS -2 kt IAS per 1000 feet Zp VNE power-off .........................................................................110 kt IAS -2 kt IAS per 1000 feet Zp Caution range ....................................................................0 – 45 kt IAS Issue 05 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-3 Rotor speed limits Power-on Maximum................................................................................. 540 RPM Green arc ..................................................................... 515 to 540 RPM Minimum.................................................................................. 515 RPM Power-off Maximum................................................................................. 610 RPM Caution range................................................................... 540-610 RPM Normal range.................................................................... 515-540 RPM Caution range................................................................... 450-515 RPM Minimum.................................................................................. 450 RPM Rotor brake operation Maximum................................................................................. 150 RPM High NR horn ...................................................................... > 594 RPM Low NR horn ....................................................................... < 466 RPM Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-4 EASA Approved Original issue Powerplant limitations Operating limitations Engine speed Maximum engine speed.........................................................2700 RPM Normal range ................................................................2585-2700 RPM Minimum engine speed, power-on .........................................2585 RPM Temperature Maximum cylinder head temperature (CHT) .................................260°C (500°F) Maximum recommended CHT for shut down................................180°C (356°F) Maximum oil temperature..............................................................118°C (245°F) Minimum recommended oil temperature before applying full power ....... ...................60°C (140°F) Oil pressure Maximum .................................................................................... 7.9 bar (115 psi) Maximum for flight....................................................................... 6.6 bar (95 psi) Minimum for take-off (CLUTCH light OFF).................................. 3.6 bar (52 psi) Minimum during idle.................................................................... 1.6 bar (25 psi) Fuel pressure Maximum .................................................................................. 0.55 bar (8 psi) Minimum .................................................................................. 0.02 bar (0.3 psi) Issue 05 Starting and warm-up range Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-5 Fuel Approved grade.............................................................. AVGAS 100LL Maximum tank capacity ................................................................. 170 L (45 U.S. gal) Unusable fuel quantity.................................................................... 1.5 L (0.4 U.S. gal) Warning : Do not rely on fuel quantity indication when Caution light is ON or EPM warning is active. Engine Oil After break-in, use multigrade oil........................................MIL-L-22851 Ashless dispersant SAE 15W50 or 20W50 During break-in (50 hours), use straight mineral oil........... MIL-L-6082B OAT Grade Above 27°C (80°F) SAE 60 Above 16°C (60°F) SAE 50 -1°C to 32°C (30°F to 90°F) SAE 40 -18°C to 21°C (0°F to 70°F) SAE 30 Below -12°C (10°F) SAE 20 Oil quantity Oil sump capacity ........................................................................... 5.7 L (6 U.S. Quarts) Minimum oil quantity for take-off..................................................... 3.8 L (4 U.S. Quarts) Gearboxes oil Use Hélicoptères Guimbal oil referenced HG30-0039 (85W140). Issue 01 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-6 EASA Approved Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-7 Indicated power on MLI The Multiple Limits Indicator displays the engine power status, based on engine manifold absolute pressure, with two limits : • Power (PWR) limit, which corresponds to the engine rated power of 108 kW (145 hp), • Throttle (FLO) limit, which corresponds to full throttle power. At sea level in standard conditions, FLO limit corresponds to an engine power of 134 kW (180 hp). − Their relative positions vary with engine inlet air temperature and altitude, − Both limits should not to be exceeded at any time, − The indicator (pointer and digits) displays power delivered by the engine in terms of margin to the first of these limits. Note 1 : The red radial PWR mark shows that the limit could be exceeded if the pilot requires too much power. He should control the flight not to exceed it. Note 2 : The red FLO arc warns the pilot that the limit cannot mechanically be exceeded in order to help him anticipate. Maximum ................................................................................................. 100 % Maximum rated...............................................................................100 % PWR Full throttle....................................................................................... 100 % FLO Transmission limitations Main Gearbox power limitation...................................... 100 % PWR on MLI Main Gearbox temperature ...................................................... Caution light PWR limit mode Maximum rated power Full throttle power Available power indication FLO limit mode Full throttle power Issue 03 Maximum rated power Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-8 EASA Approved Original issue Weight and balance limitations (Imperial units) Maximum Gross Weight ...................................................................1543 lb Point 1 ...................................................... 1036 lb................ 83.5 in Point 2 ...................................................... 1102 lb................ 83.5 in Point 3 ...................................................... 1543 lb................ 79.7 in Point 4 ...................................................... 1543 lb................ 75.4 in Point 5 ...................................................... 1213 lb................ 75.4 in Note : Rotor axis is.................................. X = 78.7 in Y = 0 in Lateral Balance diagram 75 77 79 81 83 85 Xcg, in Ycg, in -3,1 0,0 3,1 Longitudinal Weight and Balance diagram 1 3 4 5 1000 1100 1200 1300 1400 1500 75 77 79 81 83 85 Fore Aft in lb 78.7 2 Issue 05 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-9 Weight and balance limitations (metric units) Maximum Gross Weight.................................................................... 700 kg Point 1........................................................470 kg ............2120 mm Point 2........................................................500 kg ............2120 mm Point 3........................................................700 kg ............2025 mm Point 4........................................................700 kg ............1915 mm Point 5........................................................550 kg ............1915 mm Note : Rotor axis is ..............................X = 2000 mm Y = 0 mm Lateral Balance diagram -80 0 80 1900 1950 2000 2050 2100 2150 Xcg, mm Ycg, mm Issue 05 mm Longitudinal Weight and Balance diagram 5 4 3 1 450 500 550 600 650 700 1900 1950 2000 2050 2100 2150 Fore Aft kg 2 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-10 EASA Approved Original issue Sensors failures When the MASTER is switched on, the EPM carries out a self-test and displays a test page (refer to page 7-13). Only one flight should be performed after one of following parameters are displayed “Failed”, with following restrictions : Failed parameter Flight restriction OAT Use Section 5 to compute available performance Apply a margin on temperature Pressure Limit MLI to 95% PWR and 100% FLO (the smallest) T. induction Carb. heat test : control through NR drop CHT Avoid long hover. Carb. T Control carb. heat manually Use carb. heat below 80% MLI ManP Use Section 5 to compute available performance Throttle Use Section 5 to compute available performance Oil T Avoid prolonged hover. Monitor CHT Oil P Monitor CLUTCH and OIL P. lights Fuel Q Perform an accurate fuel planning MGB/TGB Chips Hand-check corresponding plug at take-off Battery charge Minimize electrical loads CO Keep cabin heat closed Carb. heat control Control carb. heat manually Use carb. heat below 80% MLI Issue 03 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-11 HEADING FOR STEER COMPASS DATE : 0 45 90 135 180 225 270 315 Placards
On cabin ceiling :
On cabin ceiling : 0 2000 4000 6000 8000 10 000 12 000 13 000 130 126 122 118 114 110 106 104 VNE POWER OFF SUBTRACT 20 kt VNE POWER ON Zp (ft) Vi (kt) IAS subtract Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-12 EASA Approved Original issue AVGAS 100LL Max. 170 Litres 45 US Gal
Above the fuel tank filler cap :
Under cabin heater control :
In clear view of all occupants : Note : if the aircraft is approved for night VFR, refer to Section 9 Supplements.
On the right and left side of central console : No hard object No hard object No hard object No hard object under seat under seat under seat under seat CLOSE IN CASE OF ENGINE FIRE Issue 02 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-13 5 kg 11 lb MAX. LOAD comply with C.G. limit MAX. LOAD comply with C.G. limit 1 kg 2 lb 40 kg 88 lb
Forward luggage compartment :
Forward luggage compartment and under pilot seat :
Main luggage compartment : AUX. 12V D.C. 5A protected 13.7 V D.C. Issue 05 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-14 EASA Approved Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Original issue EASA Approved 3-i Section 3 Emergency procedures INTRODUCTION.............................................................................................. 3-1 POWER FAILURES .......................................................................................... 3-2 General .................................................................................................. 3-2 Power failure - hover below 8 feet AGL ................................................ 3-3 Power failure during take-off .................................................................. 3-3 Other in-flight power failures .................................................................. 3-3 DITCHING ..................................................................................................... 3-4 IN-FLIGHT ENGINE RESTART ............................................................................ 3-5 ENGINE FIRE ................................................................................................. 3-6 ELECTRICAL FIRE .......................................................................................... 3-7 TAIL ROTOR FAILURE ..................................................................................... 3-8 YAW CONTROL FAILURE ................................................................................. 3-8 ENGINE GOVERNOR FAILURE .......................................................................... 3-9 EPM FAILURES ............................................................................................. 3-9 AURAL WARNINGS ....................................................................................... 3-12 EPM PARAMETERS OUT OF LIMITATIONS ........................................................ 3-12 EPM ALARMS ............................................................................................ 3-14 CAUTION / WARNING LIGHTS ........................................................................ 3-15 Hélicoptères Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES 3-ii EASA Approved Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Original issue EASA Approved 3-1 The information in section 3, emergency procedures, is approved by EASA. Introduction The following emergency procedures describe the actions the pilot must take, relative to the various possible failures that can occur. However, depending on the many variable external environments, such as the type of terrain flown over, the pilot may have to adapt to the situation according to his experience. To help the pilot in his decision process, three recommendations are used : • LAND IMMEDIATELY • LAND AS SOON AS PRACTICABLE Emergency conditions are urgent and require landing at the nearest landing site at which a safe landing can be made. • CONTINUE FLIGHT Continue flight as planned. Repair at the destination according to maintenance manual. Note: Immediate action that the pilot shall take, or main parameters are written in bold characters. Hélicoptères Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES 3-2 EASA Approved Original issue Power failures General Engine failure can be detected by : • Yaw acceleration, nose to the right, • Engine noise level decreases, • Tachometer needles desynchronization on the EPM (engine decreases) • OIL P warning on the EPM and OIL P red light coming ON. • Plasma beeper, • Rotor speed decreasing and “low NR” horn. Caution : A slow decay in engine power, caused by carburetor icing or air filter clogging, is compensated by the governor and can be overlooked by the pilot. The MLI indication will not change while in PWR mode, but will rapidly shift to FLO mode, then increase to 100%. Primary transmission failure can be detected by : • High yaw rate, nose to the right, • Engine noise level increases, • Tachometer needles desynchronization on the EPM (engine increases). Eventual engine overspeed only if the governor is OFF • Rotor speed decreasing and “low NR” horn. In case of a primary transmission failure, apply following power failure actions. Roll off the twist grip as soon as possible. Warning : Safe landing may not be possible if the power failure occurs within the “unsafe” zone of the H/V diagram (refer to section 5). Operation inside this zone should be avoided.